Gas turbine energy supplementing systems and heating systems, and methods of making and using the same
A system and method for increasing power output of a gas turbine. A method of increasing a power output of a gas turbine comprises providing an auxiliary system configured to be coupled to the gas turbine. The auxiliary system includes a natural gas engine, a compressor, and a heat exchanger fluidly coupled to the compressor. The method includes fluidly coupling the auxiliary system to a combustor case of the gas turbine. The method comprises operating the natural gas engine to drive the compressor to compress air to form compressed air and directing exhaust of the natural gas engine to the heat exchanger. The method includes heating the compressed air in the heat exchanger using the exhaust of the natural gas engine to form heated compressed air and injecting the heated compressed air into the combustor case of the gas turbine.
1. A method of increasing a power output of a gas turbine, comprising:
providing an auxiliary system configured to be coupled to said gas turbine, said auxiliary system comprising a fueled engine, a compressor, and a heat exchanger fluidly coupled to said compressor;
fluidly coupling said auxiliary system to said gas turbine;
operating said fueled engine to drive said compressor to compress air to form compressed air;
directing exhaust of said fueled engine to said heat exchanger;
heating said compressed air in said heat exchanger using said exhaust of said fueled engine to form heated compressed air; and
injecting said heated compressed air into said gas turbine to increase mass flow through said gas turbine for increasing said power output of said gas turbine.
2. The method of claim 1 , wherein said fueled engine converts fueled into energy through an exothermic reaction.
3. The method of claim 1 , wherein said fueled engine runs of natural gas.
4. The method of claim 1 , wherein said heat exchanger is a counter flow recuperator.
5. The method of claim 1 , further comprising using a portion of said heated compressed air for cooling a component of said gas turbine.
6. The method of claim 1 , further comprising using a portion of said exhaust to preheat a fuel of said gas turbine.
7. The method of claim 1 , wherein said compressor is a multi-stage intercooled compressor.
8. The method of claim 7 , wherein said air is ambient air.
9. The method of claim 1 , further comprising providing a valve between said auxiliary system and said gas turbine.